Warhead

ABSTRACT

The invention relates to a warhead comprising a first and a second part, the parts being arranged relative to one another along a longitudinal axis, the first pail comprising a first explosive section, a casing, and a plurality of projectiles enclosed in the casing. The second part comprises an element designed to control the working of the warhead as a function of a control signal. The fact that the functioning of the warhead can be controlled means that the warhead can defeat a plurality of different targets, which makes the warhead versatile.

TECHNICAL FIELD

The invention relates to a warhead.

The invention also relates to a missile which comprises the warhead.

The invention also relates to a system in which the warhead is used.

BACKGROUND ART

U.S. Pat. No. 4,638,737 describes an anti-armor missile designed todefeat an active armor placed on a target, such as a tank.

The missile is designed to first defeat the active armor on the tank bymeans of a cluster of projectiles before allowing a main charge todefeat the primary armor.

However, the missile is confined to defeating relatively large, justsuch large, heavy and slow-moving targets such as tanks, which areprovided with active armor.

The front part of the missile is designed for controlled and systematicopening, the leading projectiles continuing towards the target at acertain velocity, whilst the rear main charge is first braked by abraking force and then re-propelled in order to thereby strike thetarget later than the leading projectiles.

DISCLOSURE OF INVENTION

An object of the present invention relates to the problem of producing amore versatile warhead.

This object is achieved by a warhead comprising a first and a secondpart, the parts being arranged relative to one another along alongitudinal axis, the first part comprising a first explosive section,a casing, and a plurality of projectiles enclosed in the casing, and thesecond part comprising an element designed to control the working of thewarhead as a function of a control signal.

The second part advantageously comprises a second explosive section.

The control element is advantageously designed to detonate the firstand/or the second explosive section as a function of the control signal.

The fact that the functioning of the warhead can be controlled meansthat the warhead can defeat a plurality of different targets, whichmakes the warhead versatile.

The warhead is primarily intended to defeat cruise missiles,signal-seeking missiles, controlled glide bombs and large aircraft. Itshould nevertheless be apparent that surface targets, such as varioustypes of motorized vehicles. The proposed warhead can naturally also beused to defeat naval targets.

The warhead is capable of defeating both hard and soft small targets.The warhead is capable of defeating both hard and soft large targets.One example of a small, hard target is a glide bomb. One example of alarge, soft target is a transport plane. Selected targets can beeffectively defeated since the warhead according to one embodimentcomprises multiple explosive charges, which can be used selectively indifferent variations. The explosive sections can advantageously bedetonated at different times, independently of one another.

The warhead comprises a plurality of projectiles, the impact energy ofwhich on the target can be selected, since its impact velocity can becontrolled according to the invention.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 shows a schematic view of a warhead according to one embodimentof the invention.

FIG. 2 a shows a schematic, perspective view of a main portion accordingto one embodiment of the invention.

FIG. 2 b shows a schematic, cross-sectional view of a main portionaccording to one embodiment of the invention.

FIG. 3 shows a schematic view of a casing on a warhead in a half-openedposition according to one embodiment of the invention.

FIG. 4 shows a schematic view of a segment of the casing according toone embodiment of the invention.

FIG. 5 shows a schematic view of a second module according to oneembodiment of the invention.

FIG. 6 a shows a schematic view of a warhead according to one embodimentof the invention.

FIG. 6 b shows a schematic view of a main portion according to oneembodiment of the invention.

FIG. 7 a shows a schematic view of a segment of a casing of a warheadaccording to one embodiment of the invention.

FIG. 7 b shows a schematic view of a segment of a casing located on afront part of a warhead according to one embodiment of the invention.

FIG. 8 shows a more detailed schematic view of a segmented casingaccording to one embodiment of the invention.

FIG. 9 shows a schematic view of a warhead according to one embodimentof the invention.

FIG. 10 shows a schematic view of a second module according to oneembodiment of the invention.

FIG. 11 a shows a schematic view of a projectile according to oneembodiment of the invention.

FIG. 11 b shows a schematic view of a projectile according to oneembodiment of the invention.

FIG. 11 c shows a schematic view of a projectile according to oneembodiment of the invention.

FIG. 12 shows a schematic view of an explosive column according to oneembodiment of the invention.

FIG. 13 a shows a schematic view of a sabot according to one embodimentof the invention.

FIG. 13 b shows a schematic view of a sabot according to one embodimentof the invention.

FIG. 13 c shows a schematic view of a sabot according to one embodimentof the invention.

FIG. 14 shows a schematic representation of a dispersal pattern ofprojectiles according to one embodiment of the invention.

FIG. 15 shows a schematic view of an apparatus that is used according toone embodiment of the invention.

FIG. 16 shows a schematic view of a missile comprising a warheadaccording to one embodiment of the invention.

MODE(S) FOR CARRYING OUT THE INVENTION

FIG. 1 shows a schematic view of a warhead. 100 according to oneembodiment of the invention. The warhead as described here comprisesthree sections. A first section 110 is a main portion. The first sectionmay also be termed a first module. A second section 150 comprises anexplosive charge 160 enclosed by a casing 170. The second section mayalso be termed a second module. A third section 190 comprises, amongother things, a detonation-preventing barrier 191 between the first andsecond section. The third section 190 comprises, among other things, acontrol element 120 for controlling the detonation, and a booster 192and priming device 193. The third section is incorporated into thesecond module.

According to one embodiment the total weight of the warhead is in therange from 1 to 5 kg. The total weight of the warhead is preferably inthe range from 3 to 4 kg. According to one embodiment the total weightof the warhead is in the range from 5 to 10 kg. According to oneembodiment the total weight of the warhead is in the range from 10 to 50kg.

The first, second and third sections will be described in more detailbelow.

The warhead 100 is designed for use in a number of different situations.If the warhead is incorporated into a missile, different types of targetcan therefore be defeated. According to some embodiments of theinvention the first module 110 is thus made in such a way that it willbe capable of withstanding the penetration of a target but is alsoeasily capable of opening before striking a target. The opening beforestriking a target may occur at a distance of 30 meters from the target.Alternatively, opening may occur at a lesser or greater distance fromthe target. Opening can occur in a controlled manner. Target selectionand the mode of action can be upgraded in flight. Target selection andthe mode of action can be upgraded automatically in flight. Targetselection and the mode of action can be upgraded from a combat controlstation (not shown) or other authorized user, who is on the ground, forexample, relatively close to the target.

The warhead comprises a computer device 120, which is designed tocontrol various processes in the warhead, such as detonation and targetselection. The computer device 120 can be preprogram med. Computerdevice is another term for a control unit.

The computer device is designed for communication with a combat controlstation or other authorized user. The warhead can furthermore beequipped with a sensor system (not shown). The sensor system is designedfor communication with the computer device. One advantage of theinvention lies precisely in the fact that the computer device can bepreprogrammed with regard to target selection and desired effect, sincethe sensor system might be subject to interference from externalsources, which can result in a greater uncertainty factor. Using asimple command device, a combat control can therefore modify the targetselection and/or desired effect at a late stage in a firing procedureor, as stated, even in flight. In practice the warhead is thereforeeffective against many different types of target.

FIG. 2 a shows a main portion according to one embodiment of theinvention. The main portion is for the most part rotationallysymmetrical about a longitudinal axis x as shown in the drawing. TheX-axis is the central axis of the warhead. The main portion comprises anexplosive column 210, which extends along its longitudinal axis and istightly housed in a sabot 220. Alternatively, there may be plastic orair between the explosive column 210 and the sabot 220. The explosivecolumn 210 is therefore centrally located in the main portion. Theexplosive column 210 and the sabot 220 are rotationally symmetricalabout the x-axis.

The main portion contains aimed projectiles 230 in a number of layers asshown in the drawing. There may be just one layer. According to oneaspect of the invention the main portion comprises five layers ofprojectiles 230. The various layers of projectiles are separated bysupport rings 240. Should there be five layers of projectiles, there arefour support rings arranged in the main portion. The support rings areadvantageously made of a light metal, such as aluminum or aluminumalloy. Alternatively the support rings may be made of plastics orrubber. The support rings are designed in such a way that they lendstability to the main portion. In particular, the support rings lendstability to the main portion in flight and particularly on impact witha target. According to one embodiment the support rings are securelyattached to the sabot 220. The support rings are therefore circulardisks each having a hole therein. According to another embodiment thesupport rings are tightly joined to the sabot. According to yet anotherembodiment one or more support rings are firmly attached to the sabotwhilst one or more support rings are tightly joined to the sabot

The main portion is enclosed by an outer shell 250. The outer shell mayalso be called the casing. The casing 250 is axially segmented in itslongitudinal direction. The outer shell may comprise 10 segments 260.According to another embodiment the outer shell comprises 15 segments,but the number of segments may range from 2 to 50. Alternatively thenumber of segments is greater than 50. Another term for segment used inthe description is module. A first end of each segment is detachablyfixed to the second module 150. A second end of each segment is fixed toa locking sleeve 270 located at the second end of the main portion, thatis to say in the front section of the main portion, as shown in thedrawing. The segmented casing is therefore held together by, among otherthings, the locking sleeve 270 at the second end of the main portion.Alternatively another fastener may be used. According to one embodimentthe locking sleeve is released by the pressure effect caused bydetonation of the explosive column 210. The pressure may be caused,among other things, by expanding explosive gases. According to analternative embodiment a mechanical rod or spring may be used to releasethe locking sleeve. The mechanical spring may be controlledelectromechanically by the computer device 120. The mechanical rod maybe controlled by means of a pyrotechnic charge (not shown ). Once thelocking sleeve has been released, the casing can be opened by thepressure of the explosive column. After initial opening the effect ofambient air can also contribute to further opening in flight. The shellis easily opened and projectiles present in the main portion can bedispersed in a predefined manner. It should be clearly apparent that thecasing is designed so that it can withstand high external pressure,especially on penetrating a target, but can at the same time readilydisintegrate when one or more of the casing modules is exposed to acertain internal pressure, particularly when the explosive column isdetonated.

In their outer section the support rings 240 are each tightly housed ina respective groove arranged in the shell segments 260. The supportrings may be composed of aluminum. The support rings may be entirely orpartially enclosed in epoxy resin, plastic foam or rubber or they may besurface-treated. Each shell segment therefore has at least one groovefor each support ring. In a position in which all axial segments enclosethe first module, and the locking sleeve is furthermore locked, allsupport rings are incorporated into the respective grooves of all shellsegments on different levels. One of the functions of the support ringsis that they exercise a stabilizing effect on the effect part or theentire warhead when it penetrates a target, for example an aircraftfuselage, since they enter at an angle other than a right angle, that isto say obliquely in relation t o the direction of flight.

FIG. 2 b shows a schematic, cross-sectional view of a part of a mainportion according to one embodiment of the invention.

FIG. 3 shows a schematic view of the main portion described withreference to FIG. 2 a in a half-opened position. The segments can bereleased largely at right angles to the direction of flight. Accordingto one embodiment a rotational movement occurs about the respectivepoint at which each segment is fixed to the second module.

FIG. 4 shows a schematic view of an axial shell segment according to oneembodiment of the invention. The shell segment is accordingly a part ofthe outer shell of the main portion. The shell segment is an elongate,curved profile. At a first end 262 the shell segment is fixed to thesecond module. A first side of the shell segment is essentially smooth.The first side of the shell segment is an outer side of the shell part.A second side, which is the opposite side to the first side, has abroken structure designed to be capable of receiving support rings asdescribed above. At its second end 263 the shell segment is formed insuch a way that it can be fixed to the locking sleeve.

The casing may be composed of aluminum, steel, carbon fiber-reinforcedmaterial, glass fiber reinforced epoxy resin or plastic, to name but afew materials.

FIG. 5 shows a schematic view of the second module according to oneembodiment of the invention. The second module is rotationallysymmetrical about the x-axis. The second module contains explosive 160,such as PBX 80/20, for example, or a thermobaric charge. The explosiveis surrounded by an outer casing. The casing is preferably composed of ametal or light metal. The casing may be composed of steel. At a firstend the second module has a rear cover 152. The rear cover constitutes asection of a casing which encloses the second module. The rear cover maybe composed of a different material to the remainder of the casing.

The third section 190 is situated at a second end of the second module.The explosive is therefore situated between the rear cover 152 and thethird section 190. The third section contains electronics forcontrolling the priming device and processing control signals receivedfrom external devices. The third section also serves as or contains adetonation-preventing barrier 191. The barrier is designed to preventthe accidental or intentional detonation of explosive in the first orthe second module when they are to detonate separately or at differenttimes. If, according to one exemplary embodiment, for example, theexplosive present in the second module is detonated first, the explosivecolumn in the first module must not be detonated. The barrier ispreferably composed of a combination of different materials, so that itis capable of absorbing a large proportion of the any pressure wavegenerated.

According to one embodiment the second module has been equipped with adevice capable of producing a directed explosive effect (RSV).

When assembling the warhead, additional material may be provided inorder to reduce the detonation-transmitting effect. The additionalmaterial may consist of material having different acousticcharacteristics to the remainder of the barrier. According to oneembodiment the warhead may therefore be tailored to the function of thedetonation-preventing barrier.

One advantage of the second module is that it is capable of producing anaccelerating movement of the first module upon detonation. Detonation ofthe second module therefore boosts the speed of the front module in thedirection of movement of the warhead. The boost may be desirable incertain situations such as when engaging a receding target or in caseswhere a higher speed of the warhead projectiles before they strike thetarget is desirable. The boost may be in the range from 1 to 500 m/s.The boost is preferably in the range 200-400 m/s.

A control unit 120 is arranged in the second module. The control unit iscoupled to a first communications terminal 121. The communicationsterminal contains a first receiver 122 and a first transmitter 123,which are designed to communicate with an external second communicationsterminal 124 (not shown). The second communications terminal may belocated in a missile 1600, in which the war head is transported. Thesecond communications terminal 124 may be located on the ground andcontrolled from a combat control station. Before firing from a missilecontaining the warhead, therefore, a combat control station can transmitinformation on, among other things, target selection and how the warheadis to be used. This information can be communicated via the missile ordirectly to the warhead. The information can also be transmitted fromthe combat control to the warhead in flight, that is to say when thewarhead is on its way to a target. Communication can be achieved bymeans of a guide beam or a coded electrical signal. According to oneembodiment the communications terminals are designed for wirelesscommunication with one another. According to one embodiment thecommunications terminals are designed to communicate with one another byway of a line or data bus 126. According to one embodiment the secondmodule contains two control units. The two control units may be largelysimilar to one another. The two control units may each control adetonation of the explosive column or the explosive charge in the secondmodule.

The control unit may be preprogrammed. The control unit may contain alibrary of information on targets and different scenarios. The librarymay be used when the control unit performs an automatic targetevaluation. Further information can be supplied to the control by meansof target sensors (not shown).

Priming of the explosive column and/or the explosive 160 in the secondmodule can be initiated by a booster 192 known in the art. Priming canbe achieved by means of a detonator 193, EBW (exploding bridge wire) orEFI. The priming process is preferably controlled by the control unit120.

FIG. 6 a shows a schematic view o f a warhead 100, comprising a mainportion 110 with segmented shell 250 and an explosive column 210according to one embodiment of the invention.

According to one embodiment of the second principle the total weight ofthe warhead is in the range from 1 to 5 kg. The total weight of thewarhead is preferably in the range from 3 to 4 kg. According to oneembodiment the totals weight of the warhead is in the range from 5 to 10kg. According to one embodiment the total weight of the warhead is inthe range from 10 to 50 kg.

The enclosing shell comprises a plurality of segments 251. The number ofsegments may vary depending on which design construction is adopted. Thenumber of segments may be 2 to 4. The segments are designed to latch inone another and t o be held in a specific position by means of a band254. The segments may advantageously overlap one another in order toafford greater stability. The segments may be composed of glassfiber-reinforced epoxy resin or a light metal, such as aluminum.According to one embodiment the enclosing shell comprises 16 segmentsdistributed in four layers in an axial direction. Each layer comprisesfour segments. Each layer comprises segments of the same size as oneanother. Two adjacent segment layers have a reciprocal angular offsetwith regard to the segment joints in each segment layer. The angularoffset may be 45°, for example. The segments are fitted with an angularoffset so that their joints will not be aligned. This serves to improvethe flight characteristics of the warhead. It furthermore provides a capwhich is more stable on penetrating a target.

A band is preferably arranged around each segment layer. Each band ismade of a material which is strong enough to hold each series ofsegments together in flight. The bands are furthermore intended to breakeasily and to allow release of the segments on detonation of theexplosive column.

Means for causing the bands to break may be arranged on the warhead. Forexample, an edge may be arranged so that each band is cut on impact witha target.

Alternatively, means controlled by the control unit are designed to cuteach band as a function of a control signal received.

An inner side of each segment is advantageously formed so that theprojectiles are well-fitted into the surrounding casing. The outerprojectiles in each projectile layer must therefore be tightly housed inthe casing.

FIG. 6 b shows a more detailed schematic view of a main portionaccording to one embodiment of the invention.

FIG. 7 a shows a more detailed schematic view of a shell segmentaccording to one embodiment of the invention. The shell segment isprovided with two grooves intended for latching to segments of one ormore adjacent layers in order to form a casing which covers the firstmodule. The shell segment may also be provided with grooves in a seconddimension for latching to adjoining shell segments.

FIG. 7 b shows a schematic view of a shell segment which is located atthe second end of the main portion. The shell segment has only onegroove in a first end, as can be seen from the drawing. According tothis principle also, the segments in a layer at the second end of theeffective part may be fixed by a locking sleeve as described above andmay have grooves for latching to adjoining segments.

FIG. 8 shows a more detailed schematic view of a segmented shellaccording to one embodiment of the invention. The segmented shellaccording to the second principle allows penetration of a 5 mm Duraltarget with the effect substantially maintained.

FIG. 9 shows a schematic view of a warhead 100 according to oneembodiment of the invention. The warhead has been designed to withstandpenetration of a target in that a second module has a pressure end 900.This applies even if the target has a Dural shell. The warhead 100 has acasing of a different type to the shells described above. The shell hasa primarily cohesive function. The shell has a weight-saving function.The primary characteristic of the shell is that it will hold the firstmodule together until detonation of the explosive column occurs. Theshell may be made of plastic or aluminum. The shell may be relativelythin. Instead the head on the second module has the capacity topenetrate a larger target. The warhead here does not have any supportingrings.

FIG. 10 shows a schematic view of a second module provided with apressure end according to one embodiment of the invention. The pressureend is designed for penetration of a target.

FIG. 11 a shows a schematic view of a projectile 230 according to oneembodiment of the invention. The projectile is rotationally symmetricalabout its longitudinal axis y. The projectile is circular cylindricalwith a shape tapering from a first end towards a second end, as can beseen from the drawing. The projectile is composed of a first material1110. The first material is heavy metal. Heavy metal is an alloy and maycontain tungsten, iron, nickel and cobalt. The heavy metal may have adensity in the order of 17-18 g/mm³. The projectile is also composed ofa second material 1120. The second material is surrounded by the firstmaterial. The second material is largely located close to the first endof the projectile. The second material is a metal which is capable ofburning, such as Zr, Ti, Mg etc. or a pyrotechnic mixture, such as atracer mixture, for example. The second material is the material whichprovides the incendiary effect. The second material is preferablyignited by the detonation of the explosive column. According to a secondembodiment the second material of the projectile is ignited by means ofan ignition mechanism (not shown). According to a third embodiment thesecond material of the projectile is ignited by impact energy generatedon striking a target or the like. According to a fourth embodiment thesecond material of the projectile is ignited by an applied retardant.According to a fifth embodiment the second material of the projectile isignited by a combination of two or more of said embodiments.

According to one embodiment the projectile is 30 mm in length. Accordingto one embodiment the projectile has a diameter which is 6 mm at itsfirst end.

According to one embodiment the projectile is composed solely of a firstmaterial and the second material that provides the incendiary effect isthereby omitted.

FIG. 11 b shows a schematic view of a projectile 230 according to oneembodiment of the invention. The projectile according to this embodimentis largely the same as that described with reference t o FIG. 11 a withthe additional feature that the projectile is provided with controlfins.

According to one embodiment there are four control fins located close tothe first end of the projectile at an angle of 90° to one another.According to a variant there are three control fins at an angle of 120°to one another. The control fins may be composed of a strong, lightmaterial, such as aluminum or an aluminum alloy, or alternatively steelor heavy metal.

FIG. 11 c shows a schematic view of a projectile 230 according to oneembodiment of the invention. According to this embodiment the projectileis spherical. In accordance with the aforementioned, the projectile ismade from the first material. The projectile 230 may also have a core ofthe second material and it therefore has an incendiary effect.

FIG. 12 shows a schematic view of an explosive column 210 according toone embodiment of the invention. The explosive column is centrallylocated in the main portion. The explosive column is preferably made inone piece. The explosive may consist of PBX 80/20, octol, hexotol or thelike. The explosive column comprises circular cylindrical sections. Thelength of each of the sections is equal to the length of the variouslayers of projectiles surrounding them, with any transitional zones. Thelength of each of the sections largely is largely equal to the distancebetween corresponding support rings. The explosive column is dimensionedin such a way that on explosion it causes the projectiles to disperse ina substantially annular pattern in a radial direction. A detonation ofthe explosive column therefore means that after a certain time theprojectiles form a cluster of projectiles dispersed in one spatialplane. The depth dispersion, that is to say in the direction of flight,may be regarded as negligible. A dispersion pattern is illustrated inmore detail with reference to FIG. 14.

The explosive column is furthermore dimensioned so that it has a smallerquantity of explosive where the projectiles have a smaller massrelatively to the rest of their body, that is to at their respectivefront pointed ends, in order to achieve a more balanced dispersal of theprojectiles on detonation.

The explosive column may be divided into a number of independent layers,which can be detonated independently of one another. The various layerseach have separate priming devices.

FIG. 13 a shows a schematic view of a sabot 220 according to oneembodiment of the invention. The sabot may be made from a light metal,such as aluminum or aluminum alloy. The explosive column is tightlyhoused in the sabot. According to one embodiment the sabot is formedaround the explosive column in one manufacturing process. According toanother embodiment explosive is fed into the sabot. The sabot may be 1mm thick.

One function of the sabot is to prevent uncontrolled dispersion ofexplosive gases between the projectiles upon detonation of the explosivecolumn. The sabot is therefore intended to retain the explosive columnin a specific position and improve the projectile ejection process.

FIG. 13 b shows a schematic view of a sabot 230 according to oneembodiment of the invention.

FIG. 13 c shows a schematic view of a sabot 230 according to oneembodiment of the invention.

FIG. 14 shows a schematic representation of a two-dimensional dispersalpattern for projectiles according to one embodiment of the invention.

The explosive column is dimensioned in such a way that after detonationthe projectiles will be dispersed in a controlled manner in a radialdirection. The x-axis of the warhead is therefore aligned on a centerpoint 0 in the figure. The projectiles are preferably dispersed in anannular pattern in a radial direction to the x axis (direction of flightof the warhead). The dispersal varies as a function, for example, of thequantity of explosive and the type of explosive present in the explosivecolumn in each projectile layer, the flechette density in each layer,and the individual mass and design of the flechettes. The projectilesare preferably dispersed in such a way that the respective rings ofprojectiles are largely equidistant from one another at the calculatedtime of impact against an intended target. According to one variant theprojectiles are dispersed in such a way that they form athree-dimensional cone.

FIG. 15 shows a schematic view of an apparatus according to one aspectof the invention, comprising a non-volatile memory 720, a processor 730and a read write memory 740. The memory 720 has a first memory part 750,in which is stored a computer program for controlling the apparatus 700.The computer program in the memory part 750 for controlling theapparatus 700 may be an operating system. The apparatus 700 may beenclosed, for example, in a control unit, such as the control unit 120.

The memory 720 also has a second memory part 760, in which is stored aprogram for controlling the functioning of the warhead 100. In analternative embodiment the program for controlling the warhead 100 isstored on a separate non-volatile data storage medium 762, such as areplaceable semiconductor memory. The program may be stored in anexecutable form or in a compressed state.

Where the data-processing unit 730 is described below as running aspecial function, it should be clearly understood that thedata-processing 730 runs a special part of the program that is stored inthe memory 720 or a special part of the program that is stored in thenon-volatile recording medium 762.

The data processing unit 730 is adapted for communication with thememory 720 by means of a data bus 784 and 783. The data processing unit730 is also adapted for communication with the memory 740 by means of adata bus 785 and 783. The data processing unit 730 is furthermoreadapted for communication with the memory 762 by means of a data bus789. The data processing unit 730 is also adapted for communication witha data port 799 by means of a data bus 783 The apparatus 700 cancommunicate with the external, second communications terminal 124through the data port 799.

Various methods can be performed by the apparatus 700 by running theprogram which is stored in the memory 720 or the program which is storedin the volatile recording memory 762

FIG. 16 shows a schematic view of a missile 1600 comprising a warhead100 according to one embodiment of the invention. The missile comprisesmeans 1610 of propelling the missile in a direction of flight. The meansof propulsion 1610 may be a jet engine or a propeller, which is drivenby an engine. The missile may be designed to release the warhead fromthe means of propulsion as a function of information regarding a target.The missile can release the warhead by dividing into two or more parts,the parts being separated. Alternatively the missile is designed so thatthe warhead is released from the missile in a direction of flight, thatis to say forwards. This can be done, for example, by launching thewarhead. Alternatively, when the explosive column of the warheaddetonates, the projectiles can be shot out by the missile in a radialdirection to the direction of flight. The information may be supplied bya combat control station either by wireless or via a line.Alternatively, information may be stored in a memory in a control unit1620 in the missile. Alternatively, information may be stored in amemory 762 in the control unit present in the missile. The control unit120 in the warhead is designed for communication with the control unitin the missile. The missile can be mounted and fired from aircraft,boats or land-based vehicles, for example.

The missile may be of a fighter type. The missile may be of an attacktype.

1. A warhead (100) comprising a first and a second part (110, 150), theparts being arranged relative to one another along a longitudinal axis,the first part comprising a first explosive section (210), a casing(250), and a plurality of projectiles (230) enclosed in the casing, andthe second part comprising an element (120) designed to control theworking of the warhead as a function of a control signal.
 2. The warheadas claimed in claim 1, characterized in that the second part comprises asecond explosive section (160).
 3. The warhead as claimed in claim 1 or2, characterized in that the control element is designed to detonate thefirst and/or the second explosive section as a function of the controlsignal.
 4. The warhead as claimed in claim 3, characterized in that thecontrol element is designed to control the working of the warhead sothat the first explosive section is detonated at a first time and thesecond explosive section is detonated at a second time.
 5. The warheadas claimed in claim 4, characterized in that the first time and thesecond time are separated in time.
 6. The warhead as claimed in claim 4,characterized in that the first time occurs prior to the second time. 7.The warhead as claimed in claim 4, characterized in that the second timeoccurs prior to the first time.
 8. The warhead as claimed in any one ofclaims 1-7, characterized in that detonation of the first explosivesection results in an acceleration of the projectiles in an essentiallyradial direction to the longitudinal axis.
 9. The warhead as claimed inany one of claims 1-8, characterized in that detonation of the secondexplosive section results in an acceleration of the projectiles in adirection essentially parallel to the longitudinal axis.
 10. The warheadas claimed in any one of claims 1-9, characterized in that the casingcomprises at least two segments (260; 151), which are designed to detachfrom the warhead on detonation of the first explosive section, in orderto permit dispersal of the projectiles.
 11. The warhead as claimed inany one of claims 1-10, characterized in that the casing is segmentedinto segments (260) elongated essentially parallel to the longitudinalaxis.
 12. The warhead as claimed in any one of claims 1-l1,characterized in that the casing is segmented into a plurality ofelongate segments.
 13. The warhead as claimed in any one of claims 1-12,characterized in that the casing is held in place by means of at leastone applied band (254).
 14. The warhead as claimed in claim 12,characterized in that the elongate segments are held in place by meansof a fastening device (270) at one end of the first part remote from thesecond part.
 15. The warhead as claimed in any one of claims 1-14,characterized in that the elongate segments together form an essentiallypointed nose section on one end of the first part remote from the secondpart.
 16. The warhead as claimed in any one of claims 1-15,characterized in that the casing comprises a number of modules (251)which are arranged along the longitudinal axis.
 17. The warhead asclaimed in any one of claims 1-16, characterized in that modulesarranged up against one another are detachably fixed to one another sothat together they form the casing, and that the modules can readily bereleased from one another by an increase in pressure in the warhead. 18.The warhead as claimed in any one of claims 1-17, characterized in thatthe first explosive section is separated from the second explosivesection by means of a detonation-preventing element (191).
 19. Thewarhead as claimed in any one of claims 1-18, characterized in that thecontrol signal is transmitted by wireless means.
 20. The warhead asclaimed in any one of claims 1-18, characterized in that the controlsignal is transmitted via a line.
 21. The warhead as claimed in any oneof claims 1-18, characterized in that the control element comprises anelement (120) for storing information which represents the controlsignal.
 22. A missile (1600) comprising a warhead (100) as claimed inany one of claims 1-18 and means (1610) of propelling the missile in adirection of flight.
 23. The missile as claimed in claim 22,characterized in that the missile is further designed to release thewarhead from the means of propulsion as a function of information on atarget.
 24. A system comprising a central unit and a warhead as claimedin any one of claims 1-18, characterized in that the central unit isdesigned to generate the control signal which controls the working ofthe warhead.
 25. The system as claimed in claim 24, characterized inthat the central unit comprises a transmitter for sending the controlsignal, and that the warhead comprises a receiver for receiving thecontrol signal.